CN114466789A - Method for manufacturing a wing box for a structure of an aircraft and wing box for a structure of an aircraft - Google Patents

Method for manufacturing a wing box for a structure of an aircraft and wing box for a structure of an aircraft Download PDF

Info

Publication number
CN114466789A
CN114466789A CN202080039425.7A CN202080039425A CN114466789A CN 114466789 A CN114466789 A CN 114466789A CN 202080039425 A CN202080039425 A CN 202080039425A CN 114466789 A CN114466789 A CN 114466789A
Authority
CN
China
Prior art keywords
base
reinforcing
component
fabric
reinforcing element
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN202080039425.7A
Other languages
Chinese (zh)
Inventor
克拉斯·德容
勒内·施罗德
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Operations GmbH
Original Assignee
Airbus Operations GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Airbus Operations GmbH filed Critical Airbus Operations GmbH
Publication of CN114466789A publication Critical patent/CN114466789A/en
Pending legal-status Critical Current

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
    • B29D24/00—Producing articles with hollow walls
    • B29D24/002—Producing articles with hollow walls formed with structures, e.g. cores placed between two plates or sheets, e.g. partially filled
    • B29D24/008—Producing articles with hollow walls formed with structures, e.g. cores placed between two plates or sheets, e.g. partially filled the structure having hollow ridges, ribs or cores
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/064—Stringers; Longerons
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/02—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure
    • B29C65/022—Particular heating or welding methods not otherwise provided for
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/56—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using mechanical means or mechanical connections, e.g. form-fits
    • B29C65/60—Riveting or staking
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/065—Spars
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/12—Construction or attachment of skin panels
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/18—Spars; Ribs; Stringers
    • B64C3/185—Spars
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/18—Spars; Ribs; Stringers
    • B64C3/187—Ribs
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/20—Integral or sandwich constructions
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/26—Construction, shape, or attachment of separate skins, e.g. panels
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C2001/0054—Fuselage structures substantially made from particular materials
    • B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Manufacturing & Machinery (AREA)
  • Transportation (AREA)
  • Moulding By Coating Moulds (AREA)

Abstract

A method for manufacturing a wing box for a structure of an aircraft is proposed, the method comprising: providing a first component composed of a fiber composite material, the first component having a first base of a face type, the first base having a first inner side and a first outer side, wherein a plurality of first reinforcing elements are arranged on the first inner side and form a composite with the first base; providing a second component composed of a fiber composite material, the second component having a planar second base having a second inner side and a second outer side, wherein a plurality of second reinforcing elements are arranged on the second inner side and form a composite with the second base; superposing the first part and the second part such that the first reinforcing element is placed at least partially onto the second inner side and the second reinforcing element is placed at least partially onto the first inner side; and connecting the first reinforcing element with the second base and the second reinforcing element with the first base.

Description

Method for manufacturing a wing box for a structure of an aircraft and wing box for a structure of an aircraft
Technical Field
The invention relates to a method for producing a wing box for a structure of an aircraft (Torsyskaten) and to a wing box for a structure of an aircraft.
Background
Large-size components made of fiber composite materials can be produced by different methods. In addition to injection molding, vacuum infusion is also common. These methods are based on the use of moulds which predetermine the shape of the respective component to be produced and which are provided with a fabric (Gelege) consisting of one or more layers of a semifinished fibre product. To impregnate the fiber preform with resin, the fabric produced is typically covered with a vacuum film. In a planar component, this is rather simple, since the vacuum membrane can easily follow the planar extension of the relevant component. However, if elongated stiffening members extending parallel to each other are desired, for example on the inner side of the relevant member, the vacuum membrane must also follow the stiffening members and the gaps between them flush. Wrinkles are to be prevented in this case in order to ensure the dimensional stability and integrity of the component.
In particular in traffic aircraft which have at least in sections large-size components made of fiber composite materials, significantly more complex reinforcing components are provided in sections. In so-called wing boxes, which are designed to absorb large bending moments, the reinforcing members can also extend transversely to one another and partially intersect one another. For this reason, it is common to manufacture a shell of the face type for the manufacture of the wing box and to rivet or otherwise connect separately manufactured stiffening members to the shell. The manufacturing effort required for this is considerable and the fiber offset is dimensioned or determined accordingly when the riveted connection is produced.
Disclosure of Invention
The object of the invention is to provide a method for producing a wing box for a structure of an aircraft, in which method the effort can be reduced without resulting in design deviations or increased weight of the produced wing box.
This object is achieved by a method having the features of independent claim 1. Advantageous embodiments and developments emerge from the dependent claims and the following description.
A method for manufacturing a wing box for a structure of an aircraft is proposed, the method having: a step of providing a first component composed of a fiber composite material, the first component having a first base of a profile, the first base having a first inner side and a first outer side, wherein a plurality of first reinforcing elements are arranged on the first inner side and form a composite with the first base; a step of providing a second component composed of a fiber composite material, the second component having a planar second base having a second inner side and a second outer side, wherein a plurality of second reinforcing elements are arranged on the second inner side and form a composite with the second base; a step of superposing the first part and the second part so that the first reinforcing element is placed at least partially onto the second inner side and the second reinforcing element is placed at least partially onto the first inner side; and a step of connecting the first reinforcing element with the second base and the second reinforcing element with the first base.
Such wing boxes may be, for example, wings, horizontal stabilizers, vertical stabilizers, landing flaps or other structural members or structural components. A wing box is described as a hollow structural member configured to absorb bending moments about at least one axis. The wing box may have different shapes ranging from, more precisely, a cubic shape to a longer rectangular parallelepiped shape or a more planar shape. The walls of the wing box need not be flat but may also have a more or less pronounced curvature. In addition, the wing box is characterized in the following by two face-shaped shell-like members in the form of a first base and a second base, which are present at a distance from each other and which contain a first reinforcing element and a second reinforcing element. It is particularly advantageous to manufacture the first and second components in the manner described above.
The first base part of the surface type is provided with first reinforcing elements, and the first reinforcing elements and the first base part form a complex. As previously mentioned, this may include the manufacture of the fabric and subsequent infiltration and stiffening. For this purpose, in order to perform the infiltration and during the hardening, the closing means are arranged on the fabric. The closing means can, for example, enter the interspaces between the first reinforcing elements. Alternatively, the recess can also be temporarily covered with the reinforcing element, so that the closure device then jointly covers the textile and the reinforcing element.
This can be performed particularly advantageously when limited to the first reinforcing element or the second reinforcing element, since the flexible closing means can follow the uniformly arranged and completely penetrating interspace without wrinkles. On the other hand, the reinforcing element can also be pushed out of the first or second component in one direction after hardening.
This results in a first and a second component which can be produced simply and with common tools and which saves on the parts of the connection required in the prior art. The first base part and the first reinforcing element of the profile and the second base part and the second reinforcing element of the profile each constitute a continuous, unbonded component of the internal reinforcement. The stacking allows the manufacture of the wing box by connecting the stiffening members on one side each. The expenditure for fixing the individual components to one another is therefore substantially halved.
When using a riveted connection, approximately half of the corresponding bore is necessary, so that an improvement in the force flow and the mechanical adaptation required for the riveted connection can be expected compared to merely rented components.
In an advantageous embodiment, providing the first component or the second component comprises: forming a fabric on a mold; covering the fabric with a closure device; impregnating the fabric with a resin; hardening; and removing the closure device. In particular, the method can be carried out in the form of a vacuum infusion method or as a Resin injection Molding (RTM). The fabric is sealed all around on the mold by means of a closing device (e.g. a vacuum film) so that the fabric is hermetically and form-reliably enclosed on the mold. The term "resin" in the sense of the present invention can have any matrix material which is suitable for forming a fiber composite component with a fiber material. The matrix material can also contain hardeners (multi-component resin systems). The resin may be a thermosetting plastic in the narrow sense, for example an epoxy resin system. The use of thermoplastics is not excluded.
Forming the fabric may include: a base fabric for forming the base portion and a reinforcing fabric for forming the reinforcing elements are arranged. The joint hardening of the resin-impregnated fabric thus results in a one-piece composite component, which has particularly favorable mechanical properties in the transition region between the reinforcing component and the base part and has a relatively low weight.
In an advantageous embodiment, the first reinforcing element and/or the second reinforcing element is bonded or welded to the associated base part in order to form the composite body with the associated base part. Welding is particularly suitable for base and reinforcing elements based on materials having a thermoplastic matrix. Bonding is to a large extent possible for all materials which also comprise thermosets.
Particularly preferably, the first reinforcing element or the second reinforcing element extends in the same spatial direction. If a plurality of reinforcing elements are arranged on the respective base part, these are arranged parallel to one another. The gap between the reinforcing elements can be covered well with a flexible closure device in a shape-precise and wrinkle-free manner. The spacing can be configured variably, as can the respective structural height or depth extension of the cross-sectional profile.
Preferably, the connecting comprises: a riveted connection is made. Thus, the first and second components are riveted to each other at their connection points. However, the number of riveted connections is only about half of the riveted connections of the above-described known method for manufacturing a wing box.
In an advantageous embodiment, the second reinforcing element is oriented transversely to the first reinforcing element. The separate manufacture of the reinforcing elements on the respective base allows the subsequent nesting of the reinforcing elements for the strong structure of the wing box without making the covering fabric difficult.
The first reinforcing element is partially at least partially interrupted in order to pass the second reinforcing element. Thus, the first and second stiffening elements may form a grid within the wing box.
Preferably, the first reinforcing elements are embodied as reinforcing ribs. Further preferably, the second reinforcing element may be embodied as a beam.
The invention also relates to a wing box for a structure of an aircraft, said wing box having: a first component constructed of a fiber composite material, the first component having a first base of a face type, the first base having a first inner side and a first outer side, wherein a plurality of first reinforcing elements are arranged on the first inner side and form a composite with the first base; and a second component made of a fiber composite material, having a planar second base part having a second inner side and a second outer side, wherein a plurality of second reinforcing elements are arranged on the second inner side and form a composite with the second base part, wherein the first base part and the second base part are superposed such that the first reinforcing elements are placed at least partially on the second inner side and the second reinforcing elements are placed at least partially on the first inner side, and wherein the first reinforcing elements are connected to one another with a form fit, force fit or material fit with the second base part and the second reinforcing elements are connected to one another with a form fit, force fit or material fit with the first base part.
Particularly preferably, the first reinforcing element is embodied as a reinforcing rib, wherein the second reinforcing element is embodied as a beam, and wherein the first reinforcing element and the second reinforcing element are arranged transversely to one another.
The invention also relates to an aircraft having at least one component with a wing box according to the preceding description.
Drawings
Further features, advantages and possibilities of application of the invention emerge from the following description of an exemplary embodiment and the accompanying drawings. All described and/or illustrated features form the subject matter of the invention per se and in any combination, independently of their relationship in the individual claims or in the claims cited therein. Further, in the drawings, the same reference numerals denote the same or similar objects.
Fig. 1 shows a schematic block-based diagram of a method for manufacturing a wing box for a structure of an aircraft.
Fig. 2 shows the first part and the second part in two different views.
Fig. 3a and 3b show the manufacture of the first component on a mould.
Figure 4 shows an aircraft with a wing box.
Detailed Description
Fig. 1 shows a method 2 for manufacturing a wing box for a structure of an aircraft. According to the block diagram shown, the method may have the following steps. First, a first component made of a fiber composite material is provided 4, which has a planar first base part with a first inner side and a first outer side, wherein a plurality of first reinforcing elements are arranged 6 on the first inner side and form a composite with the first base part. Subsequently, a second component 8 consisting of a fibre composite material is provided. The second component has a planar second base with a second inner side and a second outer side, wherein a plurality of second reinforcing elements 10 are arranged on the second inner side and form a composite with the second base. Subsequently, the first and second parts are superposed 12 such that the first reinforcement element is placed at least partially onto the second inner side and the second reinforcement element is placed at least partially onto the first inner side. The first reinforcing element is then connected 14 with the second base and the second reinforcing element with the first base. Providing 4 or 8 may include: forming 16 or 18 a first fabric or a second fabric on a mold; a cover 20 or 22; impregnating 24 or 26 with a resin; hardening 28 or 30; and either 32 or 34 is removed. Forming the 16 or 18 fabric may include: the arrangement 16a is for forming the base fabric of the base and the arrangement 16b is for forming the reinforcing fabric of the reinforcing element. The connection 14 may include: a riveted connection is made.
Fig. 2 shows a first component 36 having a first base 38 of a face type. The first base portion 38 has a first exterior side 40 and a first interior side 42. On the first inner side 42, first reinforcing elements 44 are arranged, which extend parallel to one another in the same direction and are embodied, for example, as ribs. Illustratively, first base 38 and first reinforcing element 44 are formed as a continuous fabric and may be impregnated and hardened with a resin.
The second member 46 has a second base 48 having a second exterior side 50 and a second interior side 52. On which a second reinforcing element 54 embodied as a beam is located. As can be seen in the sectional view designated by a-a in the right-hand drawing plane, the first reinforcing element 44 has a plurality of interruptions 56, through which the second reinforcing elements 54 arranged transversely to the first reinforcing element 44 can extend. The first member 36 and the second member 46 are stacked and connected to each other.
Fig. 3a very schematically shows a mould 58 on which a first base fabric 60 for forming the first base 38 is arranged. Attached to the first base fabric is a first reinforcing fabric 62, which is disposed on the first base fabric 60. The first closure device 64 is placed over the fabrics 60 and 62 and terminates flush with the mold 58. The spaces between the first reinforcing fabrics 62 are also covered by the first closure device 64. Where infiltration with resin and subsequent hardening can take place. The method shown relates in particular to a vacuum infusion method.
A slightly modified variant is shown in fig. 3b, in which a first base fabric 60 and a first reinforcement fabric 62 are superposed on one another. A further first closing means 66 is selected here, which does not extend into the interstices between the first reinforcing fabrics 62. Instead, first reinforcing elements 68 are arranged there, which fill the gap in the radial direction and are covered by the first closing means 66. After hardening, these first reinforcing elements are removed again in a direction parallel to the first reinforcing fabric 62 or the resulting first reinforcing elements. To this end, it is particularly advantageous if the reinforcing fabrics 62 all extend in the same direction. The first reinforcing member 68 may then be pulled out in the same direction. The illustration relates in particular to the RTM method.
To manufacture the second part 46, a device shaped similarly to fig. 3a or 3b is used.
Fig. 4 now shows an aircraft 70 having a plurality of structural components in the form of wings 72, a horizontal tail 74 and a vertical tail 76. At least one of these structural components 72, 74 and 76 may be provided with a wing box made as previously described. Illustratively, wing box 78 is shown in phantom at the end of one of the wings 72.
It may additionally be noted that "having" does not exclude other elements or steps, and "a" or "an" does not exclude a plurality. It may furthermore be mentioned that also combinations of features already described with reference to one of the above embodiments with other features of the further embodiments described above may be used. Reference signs in the claims shall not be construed as limiting.
List of reference numerals
2 method
4 providing the first component
6 arranging a first reinforcement element
8 providing a second component
10 arranging a second reinforcement element
12 Stacking
14 connection
16 forming a first fabric
18 form a second fabric
20 covering the first fabric
22 covering the second fabric
24 impregnating the first fabric
26 impregnating the second fabric
28 stiffening the first fabric
30 hardening the second fabric
32 removing the closure device
34 removing the closure device
36 first part
38 first base
40 first outer side
42 first inner side
44 first reinforcing element
46 second part
48 second base
50 second outer side
52 second inner side
54 second reinforcing element
56 interruption part
58 mould
60 first base fabric
62 first reinforcing fabric
64 first closing means
66 first closure device
68 first reinforcing element
70 aircraft
72 wing
74 horizontal rear wing
76 vertical tail
78 wing box

Claims (13)

1. A method (2) for manufacturing a wing box (78) for a structure of an aircraft (70), having the steps of:
-providing (4) a first component (36) consisting of a fiber composite material, the first component (36) having a first base (38) of a face type having a first inner side (42) and a first outer side (40), wherein a plurality of first reinforcement elements (44) are arranged (6) on the first inner side (42) and form a composite with the first base (38),
-providing (8) a second component (46) consisting of a fiber composite material, the second component (46) having a planar second base (48) with a second inner side (52) and a second outer side (50), wherein a plurality of second reinforcing elements (54) are arranged on the second inner side (52) and form a composite with the second base (48),
-superposing (12) the first part (36) and the second part (46) such that the first reinforcement element (44) is placed at least partially onto the second inner side (52) and the second reinforcement element (54) is placed at least partially onto the first inner side (42),
-connecting (14) the first reinforcement element (44) with the second base (48) and connecting (14) the second reinforcement element (54) with the first base (38).
2. The method (2) according to claim 1,
wherein providing (4, 8) the first component (36) or the second component (46) comprises: forming (16, 18) a fabric (60, 62) on a mold (58); covering (20, 22) the fabric (60, 62) with a closure device (64, 66); impregnating (24, 26) the fabric (60, 62) with a resin; hardening (28, 30); and removing (32, 34) the closure device (64, 66).
3. The method (2) according to claim 2,
wherein forming (16, 18) the fabric (60, 62) comprises: a base fabric (60) for forming the base (38, 48) and a reinforcing fabric (62) for forming the reinforcing elements (44, 54) are arranged.
4. Method (2) according to claim 1 or 2,
wherein the first reinforcing element (44) and/or the second reinforcing element (54) are bonded or welded to the associated base (38, 48) in order to form the composite with the associated base (38, 48).
5. The method (2) according to any one of the preceding claims,
wherein the first reinforcing element (44) or the second reinforcing element (54) extends along the same spatial direction.
6. The method (2) according to any one of the preceding claims, wherein connecting (14) comprises: a riveted connection is made.
7. The method (2) according to any one of the preceding claims,
wherein the second stiffening element (54) is oriented transversely to the first stiffening element (44).
8. The method (2) according to claim 7,
wherein the first reinforcing element (44) is partially at least partially interrupted in order to pass the second reinforcing element (54).
9. The method (2) according to any one of the preceding claims,
wherein the first reinforcing elements (44) are embodied as reinforcing ribs.
10. The method (2) according to any one of the preceding claims,
wherein the second reinforcing element (54) is embodied as a beam.
11. A wing box (78) for a structure of an aircraft, having:
-a first component (36) consisting of a fibre composite material, the first component (36) having a first base (38) of a face type having a first inner side (42) and a first outer side (40), wherein a plurality of first reinforcement elements (44) are arranged on the first inner side (42) and form a composite with the first base (38); and
-a second component (46) consisting of a fibre composite material, the second component (46) having a planar second base (48) with a second inner side (52) and a second outer side (50), wherein a plurality of second reinforcing elements (54) are arranged on the second inner side (50) and form a composite with the second base (48),
wherein the first base (38) and the second base (48) are superposed such that the first reinforcement element (44) is placed at least partially on the second inner side (52) and the second reinforcement element (54) is placed at least partially on the first inner side (42),
wherein the first reinforcing element (44) and the second base (48) and the second reinforcing element (54) are connected to one another in a form-fitting, force-fitting or material-fitting manner with the first base (38).
12. Wing box (78) according to claim 11,
wherein the first reinforcing elements (44) are embodied as reinforcing ribs,
wherein the second reinforcing element (54) is embodied as a beam, and
wherein the first and second stiffening elements (44, 54) are arranged transversely to each other.
13. An aircraft (70) having at least one structural component (72, 74, 76) into which at least one wing box (78) according to claim 11 or 12 is integrated.
CN202080039425.7A 2019-08-28 2020-08-31 Method for manufacturing a wing box for a structure of an aircraft and wing box for a structure of an aircraft Pending CN114466789A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102019123012.8A DE102019123012A1 (en) 2019-08-28 2019-08-28 Method for producing a torsion box for a structure of an aircraft and a torsion box for a structure of an aircraft
PCT/IB2020/000903 WO2021038302A1 (en) 2019-08-28 2020-08-31 Method for producing a torsion box for a structure of an aeroplane and a torsion box for a structure of an aeroplane

Publications (1)

Publication Number Publication Date
CN114466789A true CN114466789A (en) 2022-05-10

Family

ID=72521569

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202080039425.7A Pending CN114466789A (en) 2019-08-28 2020-08-31 Method for manufacturing a wing box for a structure of an aircraft and wing box for a structure of an aircraft

Country Status (5)

Country Link
US (1) US20220080686A1 (en)
EP (1) EP4021800B1 (en)
CN (1) CN114466789A (en)
DE (1) DE102019123012A1 (en)
WO (1) WO2021038302A1 (en)

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1603051A (en) * 1923-01-31 1926-10-12 Theodore P Hall Airplane
US4739954A (en) * 1986-12-29 1988-04-26 Hamilton Terry W Over-lap rib joint
DE4315600C2 (en) * 1993-05-11 1996-07-25 Daimler Benz Aerospace Airbus Support structure for an aerodynamic surface
JP4574086B2 (en) * 2001-09-03 2010-11-04 富士重工業株式会社 Method for manufacturing composite wing and composite wing
US7182293B2 (en) * 2004-04-27 2007-02-27 The Boeing Company Airfoil box and associated method
WO2014065719A1 (en) * 2012-10-22 2014-05-01 Saab Ab Integral attachment of fiber reinforced plastic rib to fiber reinforced plastic skin for aircraft airfoils
ES2656854T3 (en) * 2012-11-28 2018-02-28 Airbus Operations S.L. A main support structure of a supporting surface of an aircraft
WO2014175795A1 (en) * 2013-04-25 2014-10-30 Saab Ab A method and a production line for the manufacture of a torsion-box type skin composite structure
EP2889214B1 (en) * 2013-12-31 2020-02-05 Airbus Operations, S.L. Highly integrated infused box made of composite material and method of manufacturing
GB2533582A (en) * 2014-12-22 2016-06-29 Airbus Operations Ltd Aircraft wing box, aircraft wing, aircraft and supporting member for use therein
GB201522327D0 (en) * 2015-12-17 2016-02-03 Airbus Operations Ltd Wing structure
GB2550403A (en) * 2016-05-19 2017-11-22 Airbus Operations Ltd Aerofoil body with integral curved spar-cover
US20180086429A1 (en) * 2016-09-28 2018-03-29 The Boeing Company Airfoil-Shaped Body Having Composite Base Skin with Integral Hat-Shaped Spar
EP3330174B1 (en) * 2016-12-02 2019-10-30 Airbus Operations, S.L. Aircraft stabilizer leading edge integration with torsion box and fuselage
GB2584423A (en) * 2019-05-28 2020-12-09 Airbus Operations Ltd Rib mounting assembly

Also Published As

Publication number Publication date
DE102019123012A1 (en) 2021-03-04
EP4021800A1 (en) 2022-07-06
EP4021800B1 (en) 2024-06-05
US20220080686A1 (en) 2022-03-17
WO2021038302A1 (en) 2021-03-04

Similar Documents

Publication Publication Date Title
CN101484290B (en) Method for producing a fibre composite component for aviation and spaceflight and fibre composite component obtained thereby
EP3109152B1 (en) Stiffened fuselage component as well as method and apparatus for manufacturing a stiffened fuselage component
CN101171122B (en) Method for the manufacturing a hollow fiber reinforced structural member
EP2388477B1 (en) Blade of a wind turbine
US9211689B2 (en) Composite material structures with integral composite fittings and methods of manufacture
US10858047B2 (en) Method of manufacturing partition panel for vehicles
KR20130141562A (en) Composite structures having integrated stiffeners with smooth runouts and method of making the same
JPH0239920A (en) Frame particularly for aircraft fugelage
CN102548741A (en) Method of molding complex composite parts using pre-plied multi-directional continuous fiber laminate
CN109562578A (en) The manufacturing method of composite material structure and composite material structure
KR101484203B1 (en) Fiber reinforced plastic vehicle body structure and manufacturing method thereof
CN104428127A (en) Self-stiffened composite panel and method of producing same
US10562607B2 (en) Control surface element
CN110497657A (en) For manufacturing the method for multi-layer fiber reinforced resin composite material and using the molding product of this method
US8039069B2 (en) Composite structural part formed of multiple layer fibrous preforms inter-fitted with one another and reinforced with a polymer matrix coating
CN114466789A (en) Method for manufacturing a wing box for a structure of an aircraft and wing box for a structure of an aircraft
US10807323B2 (en) Manufacture of objects having a fiber-reinforced region
US9156235B2 (en) Modular production device for integral fiber semifinished products and method for producing endless-fiber composite components made from integral fiber composite semifinished products having a hollow body structure
JP7131998B2 (en) Method for making hat-shaped stiffener preforms with undercut chamfered flanges
JP4833603B2 (en) Molding jig
EP2697044B1 (en) A method and a device for the manufacture of a fibre composite component, and a fibre composite component
WO2014156682A1 (en) Fiber-reinforced resinous vehicular floor structure and manufacturing method of same
CN110087849A (en) Fibrous structures with the fiber rod for connecting into frame
CN211334659U (en) Self-supporting composite structure for body and chassis components
US20200198756A1 (en) Fuselage component for an aircraft, method for producing a fuselage component, and aircraft

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination